New! View global litigation for patent families

US5658358A - Fuel supply system for combustion chamber - Google Patents

Fuel supply system for combustion chamber Download PDF

Info

Publication number
US5658358A
US5658358A US08222241 US22224194A US5658358A US 5658358 A US5658358 A US 5658358A US 08222241 US08222241 US 08222241 US 22224194 A US22224194 A US 22224194A US 5658358 A US5658358 A US 5658358A
Authority
US
Grant status
Grant
Patent type
Prior art keywords
vortex
flow
duct
fuel
generators
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US08222241
Inventor
Yau-Pin Chyou
Adnan Eroglu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ABB Management AG
General Electric Technology GmbH
Original Assignee
ABB Management AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Grant date

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CCOMBUSTION APPARATUS USING FLUENT FUEL
    • F23C7/00Combustion apparatus characterised by arrangements for air supply
    • F23C7/002Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B01PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01FMIXING, e.g. DISSOLVING, EMULSIFYING, DISPERSING
    • B01F5/00Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F5/04Injector mixers, i.e. one or more components being added to a flowing main component
    • B01F5/0403Mixing conduits or tubes, i.e. conduits or tubes through which the main component is flown
    • B01F5/0471Mixing conduits or tubes, i.e. conduits or tubes through which the main component is flown the additional component being introduced at the circumference of the conduit
    • B01F5/0473Mixing conduits or tubes, i.e. conduits or tubes through which the main component is flown the additional component being introduced at the circumference of the conduit with additional mixing means other than injector mixers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15DFLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00Influencing flow of fluids
    • F15D1/0015Whirl chambers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46Details, e.g. noise reduction means
    • F23D14/62Mixing devices; Mixing tubes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO MACHINES OR ENGINES OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, TO WIND MOTORS, TO NON-POSITIVE DISPLACEMENT PUMPS, AND TO GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY
    • F05B2240/00Components
    • F05B2240/10Stators
    • F05B2240/12Fluid guiding means, e.g. vanes
    • F05B2240/122Vortex generators, turbulators, or the like, for mixing

Abstract

In a fuel supply system with premixing combustion, a gaseous and/or liquid fuel is introduced as a secondary flow into a gaseous, ducted main flow. The secondary flow has a substantially smaller mass flow than the main flow. The main flow is guided via vortex generators (9) of which a plurality are arranged adjacent to one another over the periphery of the duct (20), through which flow takes place, on at least one duct wall. The secondary flow is fed into the duct (20) in the immediate region of the vortex generators (9). A vortex generator (9) has three surfaces around which flow takes place freely, which surfaces extend in the flow direction, one of them forming the top surface (10) and the two others forming the side surfaces (11, 13). The fuel is fed into the duct from nozzles which are located before, behind or in the vortex generator.

Description

BACKGROUND OF THE INVENTION

1. Field of the Invention

The invention relates to a fuel supply system for a combustion chamber with premixing combustion in which a gaseous and/or liquid fuel is introduced as a secondary flow into a gaseous, ducted main flow, the secondary flow having a substantially smaller mass flow than the main flow and the premixing duct through which flow takes place having curved walls.

2. Discussion of Background

The mixing of fuel into a combustion air flow occurring in a premixing duct takes place, as a rule, by means of the radial introduction of the fuel into the duct by means of cross-jet mixers. The momentum of the fuel, however, is so small that almost complete mixing has only taken place after a distance of approximately 100 duct heights. Venturi mixers are also used. The introduction of fuel via grid arrangements is also known. Finally, the introduction of fuel before special swirlers is also used.

The appliances operating on the basis of cross jets or layer flows either have, as a result, very long mixing lengths or demand high injection momentums. In the case of premixing at high pressure and substoichiometric mixing conditions, the danger exists of flash-back of the flame or even self-ignition of the mixture. Flow separations and dead water zones in the premixing tube, thick boundary layers on the walls or possibly extreme velocity profiles over the cross section through which flow takes place can be the cause for self-ignition in the pipe or form paths by means of which the flame can flash back into the premixing tube from the combustion zone located downstream. It is therefore necessary to pay maximum attention to the geometry of the premixing length.

SUMMARY OF THE INVENTION

Accordingly, one object of the invention is to provide, in a combustion chamber with premixing combustion, a novel measure by means of which thorough mixing of the combustion air and fuel is achieved within the shortest distance with a simultaneously even velocity distribution in the mixing zone. The measure should also be suitable for retrofitting to existing premixing combustion chambers.

This is achieved, in accordance with the invention,

in that the main flow is guided via vortex generators of which a plurality are arranged adjacent to one another over the periphery of the duct through which flow takes place on at least one duct wall, and in that the secondary flow is fed into the duct in the immediate region of the vortex generators,

in that a vortex generator has three surfaces around which flow can take place freely, which surfaces extend in the flow direction, one of them forming the top surface and the two others forming the side surfaces,

in that the side surfaces abut the same duct wall and enclose the V-angle α between them,

in that a top surface edge extending transverse to the duct through which flow takes place is in contact with the same duct wall as the side walls,

and in that the longitudinally directed edges of the top surface, which abut the longitudinally directed edges of the side surfaces protruding into the flow duct, extend at an angle of incidence θ to the duct wall.

Using the novel static mixer, which is represented by the three-dimensional vortex generators, it is possible to achieve extraordinarily short mixing lengths in the combustion chamber with a simultaneously low pressure loss. Rough mixing of the two flows has already been achieved after one complete rotation of the vortex due to the generation of a longitudinal vortex without a recirculation region, whereas fine mixing as a consequence of turbulent flow and molecular diffusion processes is present after a distance which corresponds to a few duct heights.

The advantage of the vortex generators may be seen in their particular simplicity in every respect. The element consisting of three walls around which flow takes place is completely unproblematic from the point of view of manufacture. The top surface can be joined to the two side surfaces in many different ways. The fixing of the element on flat or curved duct walls can also take place by means of simple welds in the case of weldable materials. From the point of view of fluid mechanics, the element has a very low pressure loss when flow takes place around it and it generates vortices without a dead water region. Finally, the element can be cooled in many different ways and with various means because of its generally hollow internal space.

It is appropriate to select the ratio between the height h of the connecting edge of the two side surfaces and the duct height H in such a way that the vortex generated fills the full duct height, or the full height of the part of the duct associated with the vortex generator, immediately downstream of the vortex generator.

It is useful for the two side surfaces enclosing the V-angle α to be arranged symmetrically about an axis of symmetry. Equal-swirl vortices are generated by this means.

If the two side surfaces enclosing the V-angle α form, between them, an at least approximately sharp connecting edge which forms, together with the longitudinal edges of the top surface, a point, the cross section through which flow takes place is almost unimpaired by blockage.

If the sharp connecting edge is the outlet edge of the vortex generator and if it extends at right angles to the duct wall which the side surfaces abut, the non-formation of a wake region is of advantage.

If the axis of symmetry extends parallel to the duct axis and the connecting edge of the two side surfaces forms the downstream edge of the vortex generator whereas, in consequence, the edge of the top surface extending transverse to the duct through which flow takes place forms the edge which the duct flow meets first, then two equal and opposing vortices are generated on one vortex generator. A swirl-neutral flow pattern is present in which the direction of rotation of the two vortices rises in the region of the connecting edge.

Further advantages of the invention, in particular in association with the arrangement of the vortex generators and the introduction of the secondary flow, are given in the subclaims.

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete appreciation of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:

FIG. 1 shows, diagrammatically, a perspective representation of a vortex generator;

FIG. 2 shows, diagrammatically, an embodiment variant of the vortex generator;

FIG. 3 shows, diagrammatically, the annular combustion chamber of a gas turbine with vortex generators in accordance with FIG. 1 installed;

FIG. 4 shows, diagrammatically, a partial longitudinal section through a combustion chamber along the line 4--4 in FIG. 3;

FIG. 5 shows, diagrammatically, a plurality of variants of the secondary flow guidance;

FIGS. 6a, b shows, diagrammatically, a second arrangement variant of the vortex generators in an annular combustion chamber;

FIGS. 7a, b shows, diagrammatically, a third arrangement variant of the vortex generators in an annular combustion chamber;

FIGS. 8a, b shows, diagrammatically, a fourth arrangement variant of the vortex generators in accordance with FIG. 2 in an annular combustion chamber;

FIGS. 9a, b shows, diagrammatically, a cylindrical combustion chamber with a first arrangement variant of the vortex generators;

FIGS. 10a, b shows, diagrammatically, a cylindrical combustion chamber with a second arrangement variant of the vortex generators;

FIGS. 11a, b shows, diagrammatically, a cylindrical combustion chamber with an arrangement variant of the vortex generators in accordance with FIG. 2;

FIGS. 12a, b shows, diagrammatically, an arrangement variant as in FIG. 9 with a central fuel feed;

FIGS. 13a, b shows, diagrammatically, a fuel lance equipped with vortex generators.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring now to the drawings, wherein like reference numerals designate identical or corresponding parts throughout the several views, in which the flow direction of the working media is indicated by arrows and in which elements not essential to the invention (such as casings, fastenings, conduit lead-throughs and the like) are omitted, the vortex generator which is essential for the mode of operation of the invention is described first before the actual combustion chamber is considered.

The actual duct, through which there is a main flow symbolized by the large arrow, is not shown in FIGS. 1, 2 and 5. As shown in these figures, a vortex generator consists essentially of three triangular surfaces around which flow takes place freely. These surfaces are a top surface 10 and two side surfaces 11 and 13. These surfaces extend longitudinally at certain angles in the flow direction.

The long sides of the vortex generator side walls, which consist of right-angled triangles, are fixed to a duct wall 21, preferably in a gastight manner. They are oriented in such a way that they form a joint on their narrow sides and enclose a V-angle α. The joint is designed as sharp connecting edge 16 and is at right angles to the duct wall 21 which the side surfaces abut. The side surfaces 11, 13 enclosing the V-angle α are symmetrical in FIG. 1 in shape, size and orientation and are arranged on both sides of an axis of symmetry 17. This axis of symmetry 17 has the same direction as the duct axis.

An edge 15 of the top surface 10 has a very narrow configuration and extends transverse to the duct through which flow takes place. This edge is in contact with the same duct wall 21 as the side walls 11, 13. Its longitudinally directed edges 12, 14 abut the longitudinally directed edges of the side surfaces protruding into the flow duct. The top surface extends at an angle of incidence θ to the duct wall 21. Its longitudinal edges 12, 14 form, together with the connecting edge 16, a point 18.

The vortex generator can also, of course, be provided with a bottom surface by means of which it is fastened to the duct wall 21 in a suitable manner. Such a bottom surface, however, has no relationship to the mode of operation of the element.

In FIG. 1, the connecting edge 16 of the two side surfaces 11, 13 forms the downstream edge of the vortex generator. The edge 15, of the top surface 10, extending transverse to the duct through which flow takes place is therefore the edge which the duct flow meets first.

The mode of operation of the vortex generator is as follows. When flow takes place around the edges 12 and 14, the main flow is converted into a pair of opposing vortices. The vortex axes are located in the axis of the main flow. The swirl number and the location of the vortex breakdown, where the latter is desirable at all, are determined by appropriate selection of the angle of incidence θ and the V-angle α. With increasing angles, the vortex strength and the swirl number are increased and the vortex breakdown location moves upstream into the region of the vortex generator itself. These two angles θ and α are specified, depending on the application, by design requirements and by the process itself. It is then only necessary to match the length L of the element and the height h of the connecting edge 16 (FIG. 4).

On the basis of a vortex generator in accordance with FIG. 1, FIG. 2 shows a so-called "half vortex generator" in which only one of the two side surfaces of the vortex generator 9a is provided with a V-angle α/2. The other side surface is straight and directed in the flow direction. In contrast to the symmetrical vortex generator, there is only one vortex in this case and it is generated on the arrowed side. In consequence, the field downstream of the vortex generator is not vortex-neutral and a swirl is imposed on the flow.

The vortex generators are mainly used as a mixer of two flows. The main flow, in the form of combustion air, heads toward the transversely directed inlet edges 15 in the arrowed direction. The secondary flow, in the form of a gaseous and/or liquid fuel, has a substantially smaller mass flow than the main flow. It is fed into the main flow in the immediate region of the vortex generators.

The feeding of the gaseous and/or liquid fuel (which has to be mixed into the combustion air) into the flow duct can take place in a variety of ways, as shown in FIG. 5.

As an example, the fuel can flow out into the combustion air via wall holes 22c which are arranged in echelon in the longitudinal edges 12 and 14 (or at least in their immediate region). In this case, the fuel is first fed through the duct wall 21 into the hollow inside of the vortex generator, by means which are not shown. From the wall holes 22c, it therefore passes directly into the developing vortex which rises in the injection region. There are defined flow relationships present in this case.

The fuel can also be introduced from wall holes 22a which are located in the duct wall 21 along the edge 15 of the vortex generator. The injection angle is then selected in such a way that the fuel flows around the top surface of the vortex generator as a film before it is mixed. This "cold" film forms a protective layer for the top surface against a hot main flow. This solution is specially suitable for dual-fuel operation in which both gaseous fuel and liquid fuel are mixed into the main flow and later burned. The liquid fuel, oil in the present case, is then introduced via an individual hole (not shown) opening directly at the edge 15, preferably at the same injection angle as the gas. This oil is also distributed as a protective film over the top surface before its atomization in the vortex. A slot (not shown) can be used in this case also instead of the wall holes 22b.

Wall holes 22b, through which the fuel is blown into the rising vortex, can also be provided downstream of the vortex generators.

As a departure from the possibilities shown, the fuel can also be introduced from an individual hole which is made in the region of the point 18 of the vortex generator. In this case, the medium is introduced directly into the fully formed vortex and, specifically, likewise into its rising branch.

Finally, it is obvious that all the methods or individual methods can be combined with one another.

Various different possibilities for installing the vortex generators in the premixing space of the combustion chamber are described below.

FIG. 3 shows, in a simplified manner, a combustion chamber with an annular duct 20 through which flow takes place. An equal number of vortex generators in accordance with FIG. 1 are arranged in rows in the peripheral direction on each of the duct walls 21a and 21b and without free intermediate spaces in such a way that the connecting edges 16 of two opposite vortex generators are located in the same radial. If equal heights h are assumed for the opposite vortex generators, FIG. 3 shows that the vortex generators on the inner duct ring 21b will have a smaller V-angle α. It may be recognized from the longitudinal section in FIG. 4 that compensation could be provided for this by a larger angle of incidence θ if equal-swirl vortices are desired in the inner and outer annular cross sections. In this solution, as is indicated in FIG. 3, two vortex pairs are generated, each with small vortices, and this leads to a shorter mixing length.

As shown in FIG. 4, the liquid fuel is introduced in this case via a central fuel lance 24 whose opening is located downstream of the vortex generators 9 in the region of their point 18. The introduction of the gaseous fuel takes place in two ways in this example, in accordance with the methods described in FIG. 5. On the one hand, as is indicated by arrows, it is introduced via wall holes in the vortex generators themselves and, on the other hand, it is introduced via wall holes 22b in the duct wall 21b behind the vortex generators. These wall holes are supplied by a ring main.

The fuel introduced is entrained by the vortices and mixed with the main flow. It follows the helical path of the vortices and is evenly and finely distributed in the chamber downstream of the vortices. This reduces the danger of jets impinging on the opposite wall with the formation of so-called "hot spots"--as occurs in the case of radial introduction of fuel into an unswirled flow, as mentioned at the beginning.

Because the main mixing process takes place in the vortices and is, to a large extent, insensitive to the momentum with which the secondary flow is introduced, the fuel injection can be kept flexible and matched to other boundary conditions. As an example, the momentum with which it is introduced can be kept constant over the whole of the load range. Because the mixing is determined by the geometry of the vortex generators and not by the machine load--the gas turbine power in the present example--the burner configured in this way operates in an optimum manner even under part-load conditions. The combustion process is optimized by matching the ignition delay period of the fuel to the mixing time of the vortices; this ensures minimized emissions.

Furthermore, the effective mixing produces a good temperature profile over the cross section through which flow takes place and, in addition, reduces the possibility of thermoacoustic instability appearing. The vortex generators act as a damping measure against thermoacoustic vibrations by their presence alone.

In the solutions represented in FIGS. 6 to 8, the gaseous fuel can be introduced via wall holes which are fed from ring mains fitted within the duct. It is, of course, equally possible--as a departure from the radially introduced lance represented in FIG. 4--to provide central lances for liquid fuel with a plurality of them distributed over the periphery of the annular duct.

FIGS. 6a and 6b shows a configuration similar to FIG. 3 but with smaller annular wall radii and a large duct height. Because of this, the heights of the mutually opposite vortex generators are very different.

As a rule, the height h of the connecting edge 16 will be matched to the duct height H, or the height of the duct part which is associated with the vortex generator, in such a way that the vortex generated has already reached such a size immediately downstream of the vortex generator that the full duct height H is filled. This leads to an even velocity distribution in the cross section subjected to the flow. A further criterion which can have an influence on the ratio h/H to be selected is the pressure drop which occurs when flow takes place around the vortex generator. It is obvious that as the ratio h/H increases, the pressure loss coefficient also increases.

In the vortex generators shown in FIGS. 7a and 7b the connecting edges of two opposite vortex generators are offset by half a pitch. This alters the vortex structure downstream of the vortex generators in such a way that the vortices generated on the same side have the same direction of rotation and, under certain circumstances, merge to form a large vortex which fills the complete duct cross section in the corresponding angular sector. By this means, the mixing quality can be still further improved, on the one hand, and an increased vortex life can be achieved, on the other. This solution offers the possibility (not shown) of increasing the height of the inner vortex generators so that their point can engage between the side walls of the two opposite vortex generators.

In FIGS. 8a and 8b so-called "half" vortex generators 9a are arranged in a row in the peripheral direction on both annular walls. As may be recognized from the arrows, the individual vortices--which all have the same direction of rotation--combine to form a large rotating vortex acting on the complete duct.

The three arrangements described below are extremely suitable for initial installation or as a retrofit measure in premixing chambers in which the duct 20 through which flow takes place is of circular cross section. The previous nozzle grids or mixing tubes for the gaseous fuel are simply replaced by a ring main 25 arranged inside the premixing chamber and the slots or holes 22e before the vortex generators are fed from this ring main 25. A central fuel lance could also be arranged in this composite.

As shown in FIGS. 9a and 9b four vortex generators 9 are arranged in a row in the peripheral direction on the wall 21a in such a way that no intermediate spaces are left free on the duct wall. The mode of operation of the elements in such a composite corresponds to that of the outer vortex generators in FIG. 3.

In FIGS. 10a and 10b the axis of symmetry 17 of the vortex generators 9 extends, for the same basic arrangement of the latter, obliquely to the duct axis. The two side surfaces therefore have a different V-angle relative to the main flow. Vortices with a different swirl number therefore occur on the two sides of the vortex generator. This leads to swirl adhering to the flow downstream of the elements.

The whole of the cross section through which flow takes place is swirled in the solution in accordance with FIGS. 11a and 11b. The arrangement consists of four groups, each with three vortex generators 9a in accordance with FIG. 2. The three vortex generators in one group are provided with increasing height. All the vortices generated have the same rotation.

In FIGS. 12a and 12b four Vortex generators are again arranged over the periphery. As a departure from the position shown in FIG. 9, however, the respective connecting edge 16 is now the position which the duct flow meets first. The elements are rotated by 180° as compared with FIG. 9. As may be recognized from the representation, the two opposing vortices have changed their direction of rotation. They rotate along above the top surface of the vortex generator and tend towards the wall of which the vortex generator is mounted. This solution is intrinsically suitable for the installation of a central lance 24 by means of which the fuel is introduced into the radials in which the axes of symmetry of the vortex generators extend. The fuel passes directly into the vortices rotating towards the wall.

FIGS. 13a and 13b, finally, shows a variant with vortex generators 9 which are extremely suitable as an exchange unit in cylindrical premixing chambers. In addition, it is designed for dual-fuel operation, i.e. both liquid and gaseous fuel can be mixed into the combustion air. The axial kit which can be introduced into the premixing tube (not shown) consists of a central lance 24 which is provided with vortex generators 9 on its end. The liquid fuel passes, via an oil conduit 26 arranged in the central lance 24, to the injection head from which it is injected into the duct via nozzles. The nozzles are directed, in accordance with the arrowed direction, into the line of symmetry of the vortex generators. In this way, the fuel is taken up by the rising vortices. The gaseous fuel, which is likewise 1 the central lance, passes via hollow ribs 27 into a gas ring 28 by means of which the system is centered and fixed in the tube. The fuel is added to the main flow from this gas ring 28.

The invention is not, of course, limited to the examples described and shown. With respect to the arrangement of the vortex generators in the composite, many combinations are possible without leaving the framework of the invention. The introduction of the secondary flow into the main flow can also be under-taken in a variety of ways. The variant of FIG. 9, for example, is obviously likewise suitable for use in combustion chambers of the "can" type.

Obviously, numerous modifications and variations of the present invention are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described herein.

Claims (8)

What is claimed as new and desired to be secured by Letters Patent of the United States is:
1. A fuel supply system with premixing combustion in which at least one of a gaseous and liquid fuel is introduced as a secondary flow into a gaseous, ducted main flow, the secondary flow having a substantially smaller mass flow than the main flow, the system comprising:
a premixing duct having curved walls, for guiding a main flow in a flow direction;
a plurality of vortex generators for generating vortices in the main flow, the vortex generators positioned adjacent to one another over a periphery of the premixing duct on at least one of said premixing duct walls; and
means for introducing fuel as a secondary flow into the premixing duct in an immediate region of the vortex generators,
wherein each vortex generator has three surfaces around which flow takes place freely, which surfaces extend in the flow direction, a first surface forming a top surface and a second surface and a third surface forming side surfaces,
wherein each of the side surfaces has a bottom edge abutting said premixing duct wall and an edge perpendicular to the flow direction, the perpendicular edges abutting at a connecting edge, and the side surfaces defining an acute angle about the connecting edge,
wherein the top surface has an edge extending transverse to the flow direction in contact with said premixing duct wall,
and wherein the top surface has longitudinally directed edges which abut longitudinally directed edges of the side surfaces protruding into the premixing duct, the top surface being disposed at an angle of incidence to said premixing duct wall.
2. The fuel supply system as claimed in claim 1, wherein the means for introducing a fuel is a central fuel lance having openings located in a plane located immediately downstream of the plurality of vortex generators in the flow direction.
3. The fuel supply system as claimed in claim 1, wherein the vortex generators are disposed so that the side surfaces are arranged symmetrically about an axis coinciding with the flow direction of the premixing duct.
4. The fuel supply system as claimed in claim 1, wherein each vortex generator is shaped so that the connecting edge and the longitudinally directed edges of the top surface form a point, and wherein the connecting edge extends substantially perpendicularly to the at least one premixing duct wall.
5. The fuel supply system as claimed in claim 4, wherein the longitudinally directed edges of the top surface and longitudinally directed edges of the side surfaces meet to form a substantially V-shaped profile.
6. The fuel supply system as claimed in claim 4, wherein each vortex generator is positioned symmetrically about an axis coinciding with the flow direction passing through the connecting edge, the connecting edge is disposed as a downstream edge of the vortex generator and the top surface edge extending transverse to the premixing duct flow direction is an upstream edge.
7. The fuel supply system as claimed in claim 1, wherein a ratio of a height of the vortex generators measured along the connecting edge to a premixing duct height measured parallel to the connecting edge is selected so that a vortex generated fills at least one of the premixing duct height and a height of a duct part in which the vortex generators are disposed, immediately downstream of the vortex generators.
8. The fuel supply system as claimed in claim 3, wherein the premixing duct is annular having an inner annular wall and an outer annular wall and wherein an equal plurality of vortex generators are arranged in a row in a peripheral direction both on the outer annular wall and on the inner annular wall in opposing relationship, the connecting edges of oppositely located vortex generators being in alignment.
US08222241 1993-04-08 1994-04-04 Fuel supply system for combustion chamber Expired - Lifetime US5658358A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CH108893 1993-04-08
CH1088/93 1993-04-08

Publications (1)

Publication Number Publication Date
US5658358A true US5658358A (en) 1997-08-19

Family

ID=4202193

Family Applications (1)

Application Number Title Priority Date Filing Date
US08222241 Expired - Lifetime US5658358A (en) 1993-04-08 1994-04-04 Fuel supply system for combustion chamber

Country Status (5)

Country Link
US (1) US5658358A (en)
EP (1) EP0619456B1 (en)
JP (1) JP3527278B2 (en)
DE (1) DE59404243D1 (en)
RU (1) RU2118756C1 (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6050096A (en) * 1995-09-25 2000-04-18 European Gas Turbines Ltd. Fuel injector arrangement for a combustion apparatus
US6192939B1 (en) * 1999-07-01 2001-02-27 Industrial Technology Research Institute Apparatus and method for driving a microflow
US20040037162A1 (en) * 2002-07-20 2004-02-26 Peter Flohr Vortex generator with controlled wake flow
US20040112062A1 (en) * 2002-12-17 2004-06-17 Hisham Alkabie Vortex fuel nozzle to reduce noise levels and improve mixing
US20050056313A1 (en) * 2003-09-12 2005-03-17 Hagen David L. Method and apparatus for mixing fluids
US6976508B2 (en) * 2001-01-17 2005-12-20 Trojan Technologies Inc. Flow diffusers in a UV pressurized reactor
US20070107436A1 (en) * 2005-11-14 2007-05-17 General Electric Company Premixing device for low emission combustion process
US20090266077A1 (en) * 2008-04-23 2009-10-29 Khawar Syed Mixing chamber
US20100287940A1 (en) * 2009-05-14 2010-11-18 Andrea Ciani Burner of a gas turbine
CN101012787B (en) 2006-01-24 2011-11-23 通用电气公司 Fuel injection device
US20130160423A1 (en) * 2011-12-21 2013-06-27 Samer P. Wasif Can annular combustion arrangement with flow tripping device
GB2500873A (en) * 2012-03-22 2013-10-09 Corac Energy Technologies Ltd Pipeline compression system
US20140123653A1 (en) * 2012-11-08 2014-05-08 General Electric Company Enhancement for fuel injector
US20140325989A1 (en) * 2011-01-03 2014-11-06 General Electric Company Combustor with Fuel Staggering for Flame Holding Mitigation
US20150174595A1 (en) * 2013-12-20 2015-06-25 Young Living Essential Oils, Lc Liquid diffuser

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4446541A1 (en) * 1994-12-24 1996-06-27 Abb Management Ag combustion chamber
DE59510303D1 (en) * 1995-02-03 2002-09-05 Rolls Royce Deutschland Flow guide for a gas turbine combustor
DE19507088B4 (en) * 1995-03-01 2005-01-27 Alstom premix
DE19512645A1 (en) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Fuel preparation device for gas turbine combustion chamber
DE19520291A1 (en) * 1995-06-02 1996-12-05 Abb Management Ag combustion chamber
DE19543701A1 (en) * 1995-11-23 1997-05-28 Abb Research Ltd premix
DE10250208A9 (en) * 2002-10-28 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Device for stabilizing the flame for lean premixed burner for liquid fuel in gas turbine combustors by means Turbolatorelementen in the main stream
CN102227256B (en) * 2008-11-26 2014-08-27 卡尔冈碳素公司 Method and apparatus for use of mixing elements in wastewater/ recycle water uv disinfection system
ES2462974T3 (en) * 2010-08-16 2014-05-27 Alstom Technology Ltd Reheat burner
US9435537B2 (en) * 2010-11-30 2016-09-06 General Electric Company System and method for premixer wake and vortex filling for enhanced flame-holding resistance
DE102013018146A1 (en) * 2013-12-04 2015-06-11 Astrium Gmbh Injector for a rocket combustion chamber
WO2015134009A1 (en) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Gas turbine engine with compressor exhaust flow static mixing system

Citations (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US875175A (en) * 1907-06-04 1907-12-31 Herbert F Tyler Air and gas mixer.
US1312147A (en) * 1919-08-05 Josiah mowek wallwilir
GB793325A (en) * 1954-11-24 1958-04-16 Gen Thermique Procedes Brola S Improvements in or relating to combustion apparatus
US2907557A (en) * 1952-09-23 1959-10-06 Sebac Nouvelle S A Soc Carburetor
US3244221A (en) * 1963-12-23 1966-04-05 Johns Manville Gas mixing device
GB1096624A (en) * 1964-01-30 1967-12-29 Bristol Siddeley Engines Ltd Diffusers for fluid flows
US3829279A (en) * 1973-08-20 1974-08-13 Modine Mfg Co Dual fuel burner apparatus
US3835886A (en) * 1972-12-14 1974-09-17 Rockwell International Corp Porous tube injector
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
DE2508665A1 (en) * 1975-02-28 1976-09-09 Klaus Dipl Ing Matzke Burner without air and fuel premixer - has streamlined fuel supply profiles in air flow channel to burner
US4160640A (en) * 1977-08-30 1979-07-10 Maev Vladimir A Method of fuel burning in combustion chambers and annular combustion chamber for carrying same into effect
US4164375A (en) * 1976-05-21 1979-08-14 E. T. Oakes Limited In-line mixer
US4189914A (en) * 1978-06-19 1980-02-26 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Supercritical fuel injection system
DE3520772A1 (en) * 1985-06-10 1986-12-11 Interatom Mixing appliance
WO1987000078A1 (en) * 1985-06-24 1987-01-15 Danfoil Aps Atomizer
US4812049A (en) * 1984-09-11 1989-03-14 Mccall Floyd Fluid dispersing means
US4845952A (en) * 1987-10-23 1989-07-11 General Electric Company Multiple venturi tube gas fuel injector for catalytic combustor
US4951463A (en) * 1988-09-16 1990-08-28 General Electric Company Hypersonic scramjet engine fuel injector
US4981368A (en) * 1988-07-27 1991-01-01 Vortab Corporation Static fluid flow mixing method
US5016443A (en) * 1988-09-07 1991-05-21 Hitachi, Ltd. Fuel-air premixing device for a gas turbine
GB2242734A (en) * 1990-04-04 1991-10-09 Gen Electric Lean staged combustion assembly
EP0520163A2 (en) * 1991-06-26 1992-12-30 BDAG Balcke-Dürr Aktiengesellschaft Combustion device for combustible materials
US5239831A (en) * 1990-08-20 1993-08-31 Hitachi, Ltd. Burner having one or more eddy generating devices
US5267851A (en) * 1992-03-16 1993-12-07 General Electric Company Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions
US5292244A (en) * 1992-04-10 1994-03-08 Institute Of Gas Technology Premixed fuel/air burner
US5340306A (en) * 1991-12-23 1994-08-23 Asea Brown Boveri Ltd. Device for mixing two gaseous components and burner in which this device is employed
US5380088A (en) * 1991-07-30 1995-01-10 Sulzer Brothers Limited Mixing device for small fluid quantities
US5423608A (en) * 1993-04-08 1995-06-13 Abb Management Ag Mixing apparatus with vortex generating devices
US5433596A (en) * 1993-04-08 1995-07-18 Abb Management Ag Premixing burner
US5498155A (en) * 1993-04-08 1996-03-12 Abb Management Ag Mixing and flame stabilization appliance in a combustion chamber with premixed combustion
US5513982A (en) * 1993-04-08 1996-05-07 Abb Management Ag Combustion chamber
US5518311A (en) * 1993-04-08 1996-05-21 Abb Management Ag Mixing chamber with vortex generators for flowing gases

Patent Citations (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1312147A (en) * 1919-08-05 Josiah mowek wallwilir
US875175A (en) * 1907-06-04 1907-12-31 Herbert F Tyler Air and gas mixer.
US2907557A (en) * 1952-09-23 1959-10-06 Sebac Nouvelle S A Soc Carburetor
GB793325A (en) * 1954-11-24 1958-04-16 Gen Thermique Procedes Brola S Improvements in or relating to combustion apparatus
US3244221A (en) * 1963-12-23 1966-04-05 Johns Manville Gas mixing device
GB1096624A (en) * 1964-01-30 1967-12-29 Bristol Siddeley Engines Ltd Diffusers for fluid flows
US3835886A (en) * 1972-12-14 1974-09-17 Rockwell International Corp Porous tube injector
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US3829279A (en) * 1973-08-20 1974-08-13 Modine Mfg Co Dual fuel burner apparatus
DE2508665A1 (en) * 1975-02-28 1976-09-09 Klaus Dipl Ing Matzke Burner without air and fuel premixer - has streamlined fuel supply profiles in air flow channel to burner
US4164375A (en) * 1976-05-21 1979-08-14 E. T. Oakes Limited In-line mixer
US4160640A (en) * 1977-08-30 1979-07-10 Maev Vladimir A Method of fuel burning in combustion chambers and annular combustion chamber for carrying same into effect
US4189914A (en) * 1978-06-19 1980-02-26 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Supercritical fuel injection system
US4812049A (en) * 1984-09-11 1989-03-14 Mccall Floyd Fluid dispersing means
DE3520772A1 (en) * 1985-06-10 1986-12-11 Interatom Mixing appliance
WO1987000078A1 (en) * 1985-06-24 1987-01-15 Danfoil Aps Atomizer
US4845952A (en) * 1987-10-23 1989-07-11 General Electric Company Multiple venturi tube gas fuel injector for catalytic combustor
US4981368A (en) * 1988-07-27 1991-01-01 Vortab Corporation Static fluid flow mixing method
US5016443A (en) * 1988-09-07 1991-05-21 Hitachi, Ltd. Fuel-air premixing device for a gas turbine
US4951463A (en) * 1988-09-16 1990-08-28 General Electric Company Hypersonic scramjet engine fuel injector
GB2242734A (en) * 1990-04-04 1991-10-09 Gen Electric Lean staged combustion assembly
US5239831A (en) * 1990-08-20 1993-08-31 Hitachi, Ltd. Burner having one or more eddy generating devices
EP0520163A2 (en) * 1991-06-26 1992-12-30 BDAG Balcke-Dürr Aktiengesellschaft Combustion device for combustible materials
US5380088A (en) * 1991-07-30 1995-01-10 Sulzer Brothers Limited Mixing device for small fluid quantities
US5340306A (en) * 1991-12-23 1994-08-23 Asea Brown Boveri Ltd. Device for mixing two gaseous components and burner in which this device is employed
US5267851A (en) * 1992-03-16 1993-12-07 General Electric Company Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions
US5292244A (en) * 1992-04-10 1994-03-08 Institute Of Gas Technology Premixed fuel/air burner
US5423608A (en) * 1993-04-08 1995-06-13 Abb Management Ag Mixing apparatus with vortex generating devices
US5433596A (en) * 1993-04-08 1995-07-18 Abb Management Ag Premixing burner
US5498155A (en) * 1993-04-08 1996-03-12 Abb Management Ag Mixing and flame stabilization appliance in a combustion chamber with premixed combustion
US5513982A (en) * 1993-04-08 1996-05-07 Abb Management Ag Combustion chamber
US5518311A (en) * 1993-04-08 1996-05-21 Abb Management Ag Mixing chamber with vortex generators for flowing gases

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6050096A (en) * 1995-09-25 2000-04-18 European Gas Turbines Ltd. Fuel injector arrangement for a combustion apparatus
US6192939B1 (en) * 1999-07-01 2001-02-27 Industrial Technology Research Institute Apparatus and method for driving a microflow
US6976508B2 (en) * 2001-01-17 2005-12-20 Trojan Technologies Inc. Flow diffusers in a UV pressurized reactor
US20040037162A1 (en) * 2002-07-20 2004-02-26 Peter Flohr Vortex generator with controlled wake flow
US20040112062A1 (en) * 2002-12-17 2004-06-17 Hisham Alkabie Vortex fuel nozzle to reduce noise levels and improve mixing
US6886342B2 (en) * 2002-12-17 2005-05-03 Pratt & Whitney Canada Corp. Vortex fuel nozzle to reduce noise levels and improve mixing
US20050056313A1 (en) * 2003-09-12 2005-03-17 Hagen David L. Method and apparatus for mixing fluids
US20070107436A1 (en) * 2005-11-14 2007-05-17 General Electric Company Premixing device for low emission combustion process
US8266911B2 (en) * 2005-11-14 2012-09-18 General Electric Company Premixing device for low emission combustion process
CN101012787B (en) 2006-01-24 2011-11-23 通用电气公司 Fuel injection device
US20090266077A1 (en) * 2008-04-23 2009-10-29 Khawar Syed Mixing chamber
US8424310B2 (en) * 2008-04-23 2013-04-23 Siemens Aktiengesellschaft Mixing chamber
US20100287940A1 (en) * 2009-05-14 2010-11-18 Andrea Ciani Burner of a gas turbine
US9726377B2 (en) * 2009-05-14 2017-08-08 Ansaldo Energia Switzerland AG Burner of a gas turbine
US9416974B2 (en) * 2011-01-03 2016-08-16 General Electric Company Combustor with fuel staggering for flame holding mitigation
US20140325989A1 (en) * 2011-01-03 2014-11-06 General Electric Company Combustor with Fuel Staggering for Flame Holding Mitigation
US20130160423A1 (en) * 2011-12-21 2013-06-27 Samer P. Wasif Can annular combustion arrangement with flow tripping device
US9297532B2 (en) * 2011-12-21 2016-03-29 Siemens Aktiengesellschaft Can annular combustion arrangement with flow tripping device
GB2500873A (en) * 2012-03-22 2013-10-09 Corac Energy Technologies Ltd Pipeline compression system
US20140123653A1 (en) * 2012-11-08 2014-05-08 General Electric Company Enhancement for fuel injector
US20150174595A1 (en) * 2013-12-20 2015-06-25 Young Living Essential Oils, Lc Liquid diffuser
US9358557B2 (en) * 2013-12-20 2016-06-07 Young Living Essential Oils, Lc Liquid diffuser

Also Published As

Publication number Publication date Type
JPH0771758A (en) 1995-03-17 application
EP0619456B1 (en) 1997-10-08 grant
DE59404243D1 (en) 1997-11-13 grant
JP3527278B2 (en) 2004-05-17 grant
EP0619456A1 (en) 1994-10-12 application
RU2118756C1 (en) 1998-09-10 grant

Similar Documents

Publication Publication Date Title
US5836164A (en) Gas turbine combustor
US5987889A (en) Fuel injector for producing outer shear layer flame for combustion
US5408825A (en) Dual fuel gas turbine combustor
US5060867A (en) Controlling the motion of a fluid jet
US4590769A (en) High-performance burner construction
US5319935A (en) Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection
US5816049A (en) Dual fuel mixer for gas turbine combustor
US3916619A (en) Burning method for gas turbine combustor and a construction thereof
US6532742B2 (en) Combustion chamber
US6959550B2 (en) Combustion chamber
US6019596A (en) Burner for operating a heat generator
US4781030A (en) Dual burner
US5596873A (en) Gas turbine combustor with a plurality of circumferentially spaced pre-mixers
US6968692B2 (en) Fuel premixing module for gas turbine engine combustor
US5515680A (en) Apparatus and method for mixing gaseous fuel and air for combustion including injection at a reverse flow bend
US20120192565A1 (en) System for premixing air and fuel in a fuel nozzle
US6301899B1 (en) Mixer having intervane fuel injection
US20010052229A1 (en) Burner with uniform fuel/air premixing for low emissions combustion
US5894720A (en) Low emissions combustion system for a gas turbine engine employing flame stabilization within the injector tube
US8205452B2 (en) Apparatus for fuel injection in a turbine engine
US5647215A (en) Gas turbine combustor with turbulence enhanced mixing fuel injectors
US5351477A (en) Dual fuel mixer for gas turbine combustor
US20110016866A1 (en) Apparatus for fuel injection in a turbine engine
US5687571A (en) Combustion chamber with two-stage combustion
US5408830A (en) Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines

Legal Events

Date Code Title Description
AS Assignment

Owner name: ABB MANAGEMENT AG, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CHYOU, YAU-PIN;EROGLU, ADNAN;REEL/FRAME:008211/0588

Effective date: 19940315

FPAY Fee payment

Year of fee payment: 4

AS Assignment

Owner name: ALSTOM, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ASEA BROWN BOVERI AG;REEL/FRAME:012287/0714

Effective date: 20011109

FPAY Fee payment

Year of fee payment: 8

FPAY Fee payment

Year of fee payment: 12

AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ALSTOM;REEL/FRAME:028930/0507

Effective date: 20120523